US9359903B2 - Gas turbine and guide blade for a housing of a gas turbine - Google Patents

Gas turbine and guide blade for a housing of a gas turbine Download PDF

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Publication number
US9359903B2
US9359903B2 US13/793,802 US201313793802A US9359903B2 US 9359903 B2 US9359903 B2 US 9359903B2 US 201313793802 A US201313793802 A US 201313793802A US 9359903 B2 US9359903 B2 US 9359903B2
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United States
Prior art keywords
shroud
housing
guide blade
blade
gas turbine
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US13/793,802
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English (en)
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US20140154085A1 (en
Inventor
Markus Schlemmer
Marcin Rozak
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication of US20140154085A1 publication Critical patent/US20140154085A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y02T50/673—
    • Y02T50/676—
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the present invention relates to a gas turbine, in particular an aircraft engine having a housing and at least one guide blade situated in the housing.
  • the present invention also relates to a guide blade for placement on a housing of a gas turbine and a method for manufacturing a guide blade for a housing of a gas turbine.
  • guide blades and moving blades are usually situated in alternation one after the other in a housing in the compressor and turbine stages.
  • Moving blades form the moving and rotating part of the gas turbine via which the flowing operating medium is either compressed or depressurized.
  • the flow created by the moving blades may be forwarded in a defined manner.
  • Guide blades for gas turbines usually include, in addition to a turbine blade, at least one radially outer shroud, which is situated on the turbine blade of the guide blade and forms an aerodynamic flow path limitation for the operating medium of the gas turbine in the area of the housing wall.
  • the radially outer shroud has a surface area running essentially perpendicularly to the surface of the turbine blade.
  • guide blades On the side of the shroud facing away from the aerodynamic flow path, guide blades often include shroud holding devices with the aid of which the guide blades are secured on the housing in the area of their radially outer shroud.
  • Another alternate or additional object of the present invention is to create a guide blade for a housing of such a gas turbine and a method for manufacturing such a guide blade.
  • the present invention provides a gas turbine, a guide blade and a method for manufacturing a guide blade for a housing of a gas turbine.
  • a gas turbine according to the present invention has at least one guide blade situated in a housing and having a shroud configuration as well as a turbine blade extending radially inward from the shroud configuration.
  • the shroud configuration has a radially outer shroud and a shroud holding device with the aid of which the shroud is secured on the housing.
  • the geometric design and the position of the air passage channel in the housing may be optimized for the particular intended purpose.
  • the geometric design and contour of the air passage channel are fundamentally unlimited.
  • multiple air passage channels may be distributed over the circumference of the housing, thus permitting a particularly precisely adjustable air and gas throughput.
  • the air passage channel permits in particular an improved gas admission and cooling of additional housing components such as, for example, guide blade rings situated downstream and the like.
  • the gas turbine may be designed as an aircraft engine, for example.
  • the shroud holding device includes at least one shroud hook on a side of the shroud opposite the turbine blade, with the aid of which the shroud is secured on the housing.
  • the shroud hook may fundamentally include one or more air passage channels or may be designed to be free of air passage channels.
  • it may be provided for the shroud holding device to include two or more shroud hooks, so that a particularly mechanically stable connection of the guide blade to the housing is made possible.
  • the air passage channel is designed in the form of a slot and/or having a circular arc shape and/or an elliptical arc shape and/or a rectangular and/or circular and/or elliptical cross-section in at least some areas. This permits particularly good control of the air and gas throughput.
  • these designs of the air passage channel permit a reduction in the stress concentrations on the radially outer shroud.
  • the shroud configuration is designed in one piece with the turbine blade and/or is attached to the turbine blade.
  • the guide blade may be designed to be particularly flexible and secured on the housing.
  • multiple guide blades are interconnected via their shroud configurations and form a guide blade segment and/or a guide blade ring.
  • the number of joints/gaps and thus also the gap losses are reduced in relation to individual blades in that multiple guide blades are combined into one segment or one cluster having two or more blades per unit. Less attack area is available to the aggressive hot gases, which improves the durability on the whole.
  • the situation is similar for a complete guide blade ring.
  • the guide blades form mechanically stable units due to their connection, so that relative movements and wear are reduced.
  • At least two adjacent shroud holding devices each include a groove in which a sealing element is situated in a form-locked manner. Therefore neighboring shroud holding devices or guide blades may be joined together by a type of tongue-and-groove connection, so that a sealing plate, for example, may be used as the sealing element.
  • the sealing element includes at least one air passage channel
  • the air throughput may take place here in the connecting area of two guide blades but the air passage channel in the sealing element is to be designed in such a way that there is no flow passage through the shroud during operation of the gas turbine but instead only through the shroud holding device.
  • the housing of the gas turbine includes a gas guidance system with the aid of which gas passing through the air passage channel during operation of the gas turbine is guided to housing components situated downstream from the air passage channel with respect to a predefined direction of flow of the housing.
  • the leakage flow which is adjustable in a targeted manner with the aid of the at least one air passage channel may be used for gas admission to additional guide blade stages, holders and the like situated on the housing.
  • the at least one guide blade is situated in the area of a compressor and/or in the area of a turbine.
  • the advantages of the guide blades described above such as the improved gas admission and cooling of additional housing components may optionally be implemented on the compressor side and/or on the turbine side of the gas turbine.
  • the at least one guide blade is therefore built into the housing area of the compressor or of the turbine and guides the working medium onto the moving blades of the compressor and/or of the turbine during operation of the gas turbine.
  • Another aspect of the present invention relates to a guide blade for placement on a housing of a gas turbine, the guide blade having a shroud configuration which includes a radially outer shroud in the installed state and a shroud holding device, with the aid of which the shroud is securable on the housing.
  • the guide blade according to the present invention has a turbine blade extending radially inward from the shroud configuration.
  • the guide blade together with at least one and preferably three additional guide blades forms a guide blade segment.
  • the number of joints/gaps and thus also the gap losses are reduced in relation to individual blades in that multiple guide blades are combined to form one segment or one cluster having two or more blades per unit. Less attack area is also offered to the aggressive hot gases, which improves durability on the whole.
  • the guide blades form mechanically stable units due to their connection, so that relative movements and wear are reduced. Furthermore, the segments may be joined together easily to form a complete guide blade ring.
  • Another aspect of the present invention relates to a method for manufacturing a guide blade for a housing of a gas turbine, the guide blade including a shroud configuration having a radially outer shroud in the installed state and having a shroud holding device with the aid of which the shroud is securable on the housing.
  • the guide blade includes a turbine blade extending radially inward from the shroud configuration.
  • FIG. 1 shows a schematic perspective view of a guide blade segment including four guide blade segments according to the present invention for a housing of gas turbine;
  • FIG. 2 shows an enlarged detail of a shroud area II shown in FIG. 1 ;
  • FIG. 3 shows a top view of the guide blade segment
  • FIG. 4 shows an enlarged frontal view of the shroud area IV shown in FIG. 3 .
  • FIG. 1 shows a schematic perspective view of a guide blade segment 10 for a housing of a gas turbine designed as an aircraft engine and explained below in conjunction with FIG. 2 , which shows an enlarged detail of a shroud area II shown in FIG. 1 .
  • Guide blade segment 10 here includes four guide blades 12 according to the present invention.
  • Guide blades 12 include a shared radially inner shroud 14 and a shared radially outer shroud 16 .
  • Four turbine blades 18 of guide blades 12 extend between inner shroud 14 and outer shroud 16 .
  • Radially outer shroud 16 is part of a shroud configuration 21 , shroud configuration 21 additionally including a shroud holding device 23 with the aid of which shroud 16 and the entire guide blade segment 10 may be secured on the housing of the gas turbine.
  • Shroud holding device 23 therefore includes a shroud hook 22 situated in the area of profile inlet edges 20 of turbine blades 18 on the side facing away from turbine blades 18 and a shroud hook 26 situated in the area of profile outlet edges 24 of turbine blades 18 .
  • shroud hook 22 includes an air passage channel 28 .
  • air passage channel 28 which may also be referred to as a “fingernail slot,” is designed essentially in the form of a trough having a circular arc-shaped cross section.
  • the air throughput which is adjustable with the aid of air passage channel 28 in the area of outer shroud 16 , may be used within the housing for gas admission and for cooling of housing components situated downstream in the direction of flow, such as following guide blade stages and the like.
  • the housing may include, for example, a gas guidance system 100 , shown schematically, with the aid of which gas passing through air passage channel 28 during operation of the gas turbine is guided to housing components which are situated downstream from air passage channel 28 with respect to a predefined direction of flow of the housing.
  • air passage channel 28 In addition to a targeted adjustability of the air throughput during operation of the aircraft engine, air passage channel 28 also advantageously ensures a reduction in the stress concentrations on shroud configuration 21 .
  • a particularly effective reduction in stress concentrations is achieved in particular by air passage channels 28 having a round, elliptical, ring segment or elliptical-segment-shaped cross section.
  • the geometry of air passage channel 28 is fundamentally unlimited.
  • air passage channel 28 designed on the left edge of guide blade segment 10 is designed in another position, for example, at the center or on the right edge of guide blade segment 10 and/or that only some of guide blades 12 or guide blade segments 28 installed in the housing include an air passage channel 28 and/or that guide blade segment 10 includes multiple air passage channels 28 .
  • Guide blade segment 10 shown here is manufactured in one piece by master forming. Alternatively, for example, it may also be provided for guide blades 12 to be manufactured individually and assembled to form guide blade segment 10 or a complete guide blade ring and subsequently welded together.
  • FIG. 1 also shows a side groove 25 extending on the side of shroud holding device 23 from upstream shroud hook 22 over a subarea of shroud 16 to downstream shroud hook 26 .
  • a part of shroud holding device 23 such as, for example, a sealing plate 125 , shown schematically, may be inserted in a form-locked manner into groove 25 .
  • This makes it possible to join neighboring shroud holding devices 23 and guide blade segments 10 in a type of tongue-and-groove connection.
  • the sealing element also includes an air passage channel 28 through which the air throughput takes place in the connecting area of two guide blades 12 or guide blade segments 10 .
  • air passage channel 28 should be designed only in those areas of the sealing element which come to lie in the area of one of shroud hooks 22 , 26 in the installed state of the sealing element.
  • the sealing element should not be designed in such a way that hot gases, for example, are able to pass between adjacent shrouds 16 .
  • FIG. 3 shows a top view of guide blade segment 10 . It is apparent that shroud hook 26 which is situated downstream in the direction of flow does not have an air passage channel 28 , in contrast with upstream shroud hook 22 . However, it should be emphasized that downstream shroud hook 26 may fundamentally also include one or multiple air passage channels to adjust the air throughput. In addition, it is apparent that a reinforcing structure 30 , which is elevated in relation to the surface of shroud 16 , is formed between shroud hooks 22 , 26 .
  • FIG. 4 shows an enlarged frontal view of shroud area IV shown in FIG. 3 .
  • This shows in particular the circular arc-shaped cross-section geometry of air passage channel 28 in shroud hook 22 .
  • An alternative design of air passage channel 28 is indicated by reference numeral 28 ′ which has a rectangular cross-section geometry.
  • the alternative embodiment of air passage channel 28 ′ would allow a greater air throughput accordingly due to its larger cross-sectional area in comparison with the trough-shaped air passage channel 28 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/793,802 2012-03-12 2013-03-11 Gas turbine and guide blade for a housing of a gas turbine Active 2034-12-20 US9359903B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12159013.7A EP2639408B1 (de) 2012-03-12 2012-03-12 Gasturbine, Leitschaufel für ein Gehäuse einer Gasturbine sowie Verfahren zur Herstellung einer Leitschaufel
EP12159013.7 2012-03-12
EP12159013 2012-03-12

Publications (2)

Publication Number Publication Date
US20140154085A1 US20140154085A1 (en) 2014-06-05
US9359903B2 true US9359903B2 (en) 2016-06-07

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US13/793,802 Active 2034-12-20 US9359903B2 (en) 2012-03-12 2013-03-11 Gas turbine and guide blade for a housing of a gas turbine

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EP (1) EP2639408B1 (es)
ES (1) ES2731206T3 (es)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3228826B1 (de) * 2016-04-05 2021-03-17 MTU Aero Engines GmbH Dichtungssegmentanordnung mit steckverbindung, zugehörige gasturbine und herstellungsverfahren

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB799675A (en) 1955-10-13 1958-08-13 Bristol Aeroengines Ltd Improvements in or relating to axial flow gas compressors and turbines
US4767260A (en) * 1986-11-07 1988-08-30 United Technologies Corporation Stator vane platform cooling means
US6227798B1 (en) 1999-11-30 2001-05-08 General Electric Company Turbine nozzle segment band cooling
US20090129917A1 (en) * 2007-11-13 2009-05-21 Snecma Sealing a rotor ring in a turbine stage
FR2954401A1 (fr) 2009-12-23 2011-06-24 Turbomeca Procede de refroidissement de stators de turbines et systeme de refroidissement pour sa mise en œuvre

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Publication number Priority date Publication date Assignee Title
US6932568B2 (en) * 2003-02-27 2005-08-23 General Electric Company Turbine nozzle segment cantilevered mount

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Publication number Priority date Publication date Assignee Title
GB799675A (en) 1955-10-13 1958-08-13 Bristol Aeroengines Ltd Improvements in or relating to axial flow gas compressors and turbines
DE1042828B (de) * 1955-10-13 1958-11-06 Bristol Aero Engines Ltd Axialverdichter
US4767260A (en) * 1986-11-07 1988-08-30 United Technologies Corporation Stator vane platform cooling means
US6227798B1 (en) 1999-11-30 2001-05-08 General Electric Company Turbine nozzle segment band cooling
US20090129917A1 (en) * 2007-11-13 2009-05-21 Snecma Sealing a rotor ring in a turbine stage
FR2954401A1 (fr) 2009-12-23 2011-06-24 Turbomeca Procede de refroidissement de stators de turbines et systeme de refroidissement pour sa mise en œuvre
US20120257954A1 (en) 2009-12-23 2012-10-11 Turbomeca Method for cooling turbine stators and cooling system for implementing said method

Non-Patent Citations (3)

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Title
Leishman et al.: Effects of bleed rate and endwall location on the aerodynamic behavious of a circular hole bleed off-take, Proceedings of ASME Turbo Expo 2004: Power for Land, Sea and Air Jun. 14-17, 2004, Vienna, Austria, 14 pages.
Leishman et al: "Mechanism of the interaction of a ramped bleed slot with the primary flow," Proceedings of GT2005 ASME Turbo Expo 2005: Power for Land, Sea and Air Jun. 6-9, 2005, Reno-Tahoe, Nevada, USA, 12 pages.
Wellbron et al.: Bleed Flow interactions with an axial-flow compressor poerstream,: AIAA/ASME/SAE/ASEE Joint propulsion conference & Exhibit, Jul. 2002, Indianappolis, Indiana.

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Publication number Publication date
ES2731206T3 (es) 2019-11-14
EP2639408A1 (de) 2013-09-18
EP2639408B1 (de) 2019-05-08
US20140154085A1 (en) 2014-06-05

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